# @ A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

7 DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : 1 of 4 Printed in FRANCE © AIRBUS, 2007 All rights reserved AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 

# MANDATORY MANDATORY MANDATORY

ATA SYSTEM : 57 TITLE : WINGS - INSPECT AREA AROUND OVERWING REFUELLING APERTURE AT RIBS 13-14 MODIFICATION No. : None This page transmits Revision No. 04 of Service Bulletin No. A310-57-2006. ADDITIONAL WORK No additional work is required by this revision for aircraft inspected by any previous issue. REASON This revision is issued to include all A310 aircraft in the effectivity. The effectivity has been extended due to the extended service goal conditions which now require post modification 05891, 05980 and 05981 aircraft to be inspected. Layout changes due to computerization of this revision are not identified. CHANGES SUMMARY : — REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES . Reason for the extension of the effectivity included. — EFFECTIVITY . Effectivity expanded to include all A310 aircraft. — MANPOWER . Manpower defined by Configs. — Figure . Summary Figure added. PLANNING INFORMATION :

# @ A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved — EFFECTIVITY . 1.A. Effectivity expanded to include all A310 aircraft and to include effectivity by MSN configuration. — REASON — History . 1.C.(1) Reason for extension of the effectivity included. — Objective/Action . 1.C.(2) Visual inspection included for A310-200 aircraft after Mod. No. 05891H5128 and Mod. No. 05981H5131 and all A310-300 aircraft. — Advantages . 1.C.(3) Accomplishment of SB A310-57-2020 as an advantage added. — DESCRIPTION . 1.D. Configs included. — COMPLIANCE — Accomplishment Timescale . 1.E.(2) Standard sentence added. Defined by Configs. — APPROVAL . 1.F. Approval statement updated. — MANPOWER . 1.G. Defined by Config. and inspection method. Standard sentence updated. — REFERENCES . 1.J. AMM and SRM references added. MATERIAL INFORMATION : — LIST OF MATERIALS - OPERATOR SUPPLIED . 2.D. Operator supplied material added. ACCOMPLISHMENT INSTRUCTIONS : — GENERAL . 3.A. Standard Warnings added.

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# @ A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved — Preparation . 3.A.(1) Configs added and worksteps defined. — Standard Practices . 3.A.(2) Standard practices added. — INSPECTION . 3.B.(1) Config. 01 added. . 3.B.(2) Worksteps for Config. 02 thru 03 added. . 3.B.(3) Worksteps for Config. 04 added. . 3.B.(4) Worksteps for Config. 05 added. — REPAIR . 3.C.(1) Config. 01 added. . 3.C.(1)(a) FC and FH changed. . 3.C.(2) Worksteps for Config. 02 and 03 added. Repair instructions updated. . 3.C.(3) Worksteps for Config. 04 added. Repair instructions updated. . 3.C.(4) Worksteps for Config. 05 and Config. 06 added. — TESTS . 3.D. Test paragraph added. — CLOSE-UP . 3.E. Close-up paragraph added. — Figure 1 . Config. 01 added to title. — Figure 2 . Config. 01 added to title. — Figure 3 . New Fig. added for Configs 02 and 03. — Figure 4 . New Fig. added for Config. 04.

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# @ A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved — Figure 5 . New Fig. added for Config. 05 and Config. 06. FILING INSTRUCTIONS This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete document. Put this Revision Transmittal Sheet in front of the Service Bulletin. HISTORY OF PREVIOUS REVISIONS If information is required for Revisions issued previous to this, please check your copies of Revision Transmittal Sheets or contact AIRBUS. REVISION SEQUENCE ORIGINAL : Aug 13/86 REVISION No. : 01 — Apr 08/93 REVISION No. : 02 — Mar 28/95 REVISION No. : 03 — May 02/96 REVISION No. : 04 — May 21/07

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# @ A310 SERVICE BULLETIN SUMMARY

7 DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : 1 of 4 Printed in FRANCE © AIRBUS, 2007 All rights reserved AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 This summary is for information only and is not approved for modification of the aircraft 

# MANDATORY MANDATORY MANDATORY

ATA SYSTEM : 57 TITLE : WINGS - INSPECT AREA AROUND OVERWING REFUELLING APERTURE AT RIBS 13-14 MODIFICATION No. : None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During structural testing of the wing, fatigue cracks were found that started from the attachment holes around the refuelling aperture in the wing top skin between ribs 13 and 14. On A310-200 aircraft modification 05891H5128 (Service Bulletin A310-57-2020) introduced a redesigned refuelling cap which does not require this type of attachment. It has a larger diameter aperture which removes the existing holes from which cracks originate. On some A310-200 and on all A310-300 aircraft, production modifications 05980H5130 and 05981H5131 introduced a similar design of refuelling cap as that introduced by modification 05891H5128. For A310-200 aircraft that are before modification 05891H5128 (Service Bulletin A310-57-2020), this Service Bulletin requires mandatory High Frequency Eddy Current (HFEC) inspections to be carried out in order to detect cracks in the attachment holes around the overwing refuelling aperture. The effectivity of this Service Bulletin has been extended to include all A310 aircraft upto the extended service goal (ESG). An ESG study has shown that aircraft after modifications 05891H5128, 05980H5130 and 05981H5131 will now need detailed visual inspections in the area of the refuelling aperture in the wing top skin between ribs 13 and 14. For A310-200 aircraft after modification 05891H5128 (Service Bulletin A310-57-2020) and modification 05981H5131 and all A310-300 aircraft, a detailed visual inspection is required of the external top skin in the immediate area surrounding the refuelling aperture and also internally for cracks in the adjacent stringer 7 and stringer 8. For A310-200 aircraft that are before modification 05891H5128 (Service Bulletin A310-57-2020), if cracks are found during the HFEC inspection from the attachment holes which extend away from the direction of the aperture, the

# @ A310 SERVICE BULLETIN SUMMARY

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved embodiment of the modification in its standard form will not be possible. Remedial action will then consist of either a variation of Mod 05891H5128 (Service Bulletin A310-57-2020), for short cracks, or a repair involving a reinforcing plate for longer cracks. On A310-200 aircraft after modification 05891H5128 (Service Bulletin A310-57-2020) and modification 05981H5131 and all A310-300 aircraft, if cracks are found during the detailed visual inspections they must be reported to AIRBUS. Further advice from AIRBUS will be required before the next flight. Timely detection of cracks may reduce the necessity of carrying out non standard repairs. When Service Bulletin A310-57-2020 (Mod. No. 05891H5128) has been accomplished, HFEC inspections are replaced by DVI.

EFFECTIVITY This Service Bulletin is applicable to these operators : 34W 58X 82Z 85Z 99Y A1L ABD AIC ARG BAF BBC BLM CFC CSA DAH DGA DRD F2I FDX GAF IRA IRM IYE JAB JAV KAC KYV MGL MPD MPJ MWA PIA QAF QSC R1T RJA ROT RZO S8G SBI SGX SUD TAP THY TSC UAE UZB WHT CONCURRENT REQUIREMENTS None REFERENCES/REPERCUSSIONS TFU : None OEB : None AOT : None SIL : None LIFE LIMIT : None LINE MAINTENANCE AFFECTED : No OTHERS : None EVALUATION TABLE COMPLIANCE MANDATORY CANCELS INSPECTION SB No AD Yes A/C OPERATION AFFECTED No RELIABILITY AFFECTED No PAX COMFORT AFFECTED No COST SAVING No ETOPS AFFECTED No STRUCTURAL LIFE EXTN No VENDOR SB INVOLVED No KIT PRICE (USD) No kit DEFUEL/VENTING Yes

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# @ A310 SERVICE BULLETIN SUMMARY

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NATURE OF THE WORK AIRCRAFT : Yes EQUIPMENT : No HARD : No SOFT : No OBRM : No MANPOWER Config. 01

Config. 02 thru Config. 06

MATERIAL INFORMATION AIRCRAFT DATA None APPENDICES None TOTAL MANHOURS 52.0 ELAPSED TIME (HOURS) 26.0

TOTAL MANHOURS 20.5 ELAPSED TIME (HOURS) 11.0

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# @ A310 SERVICE BULLETIN SUMMARY

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 4

# @ A310 SERVICE BULLETIN

7 DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : 1 of 26 Printed in FRANCE © AIRBUS, 2007 All rights reserved AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 

# MANDATORY MANDATORY MANDATORY

ATA SYSTEM : 57 TITLE : WINGS - INSPECT AREA AROUND OVERWING REFUELLING APERTURE AT RIBS 13-14 MODIFICATION No. : None This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with any information contained in it. It is delivered on the express condition that said document and the information contained in it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any manner (except for the purposes of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without AIRBUS' prior written consent. 1. PLANNING INFORMATION A. EFFECTIVITY (1) Models 310-203 310-204 310-222 310-304 310-308 310-322 310-324 310-325 (2) Aircraft (a) Effectivity by MSN This Service Bulletin is applicable to aircraft MSN : 0162 0172 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251 0254 0257 0260 0264 0267 0273 0278 0281 0283 0288 0291 0293 0297 0300 0303 0309 0313 0316 0318 0320 0326 0331 0333 0335 0338 0339 0342 0343 0345 0346 0349 0353 0355-0357 0359 0360 0362 0364 0367 0369 0370 0372 0375 0378 0379 0386 0389 0390 0392 0394 0397 0399 0400 0406 0407 0410 0413 0416 0418 0419 0421 0422 0425 0427-0431 0434 0436 0437 0439 0441 0444-0449 0451-0458 0467 0468 0472 0473 0475 0476 0478 0480-0492 0494-0503 0519 0520 0522-0524 0526 0527 0531 0534 0535 0537-0539 0541 0542 0544 0545 0547-0552 0562 0564 0565 0567 0568 0571 0573 0574 0576 0585-0595 0597-0600 0620 0622 0624 0634 0636 0638 0640 0642 0644 0646-0654 0656 0658 0660 0661 0663 0665 0667 0669 0671 0672 0674 0676 0678 0680 0682

# @ A310 SERVICE BULLETIN

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 0684 0686 0687 0689 0691 0693 0695 0697 0698 0700 0702 0704 0706 (b) Effectivity by Operator The Operator/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to AIRBUS. Any future changes resulting from transfer of an aircraft from one operator to another will not be reflected in this list unless the Service Bulletin is revised for another reason. OPERATOR MSN 34W 0399 58X 0431 82Z 0550 0551 85Z 0524 99Y 0489 A1L 0648 ABD 0624 AIC 0392 0406 0407 0413 0428 0429 0501 0538 0544 0548 0598 0654 0665 0669 0680 0684 0693 0695 0697 ARG 0640 0686 BAF 0367 0372 BBC 0594 0650 0698 0700 BLM 0488 CFC 0425 0441 0444 0446 0482 CSA 0564 0567 0672 0674 DAH 0291 0293 DGA 0418 0421 0422 DRD 0527 F2I 0309 0320 FDX 0162 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251 0254 0257 0260 0264 0267 0273 0278 0281 0283 0288 0297 0303 0313 0316 0318 0326 0331 0333 0335 0339 0342 0343 0345 0346 0349 0353 0355 0356 0359 0360 0362 0364 0369 0378 0394 0397 0400 0439 0449 0452 0454 0456 0457 0458 0467 0492 0500 0534 0539 0542 0549 0552 0589 0593 0634 0638 GAF 0434 0484 0498 0499 0503 0522 0523 IRA 0338 0370 0375 0379 0389 0390 0436 0671 IRM 0537 0586 IYE 0535 0568 0702 0704 JAB 0419

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# @ A310 SERVICE BULLETIN

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (c) Effectivity by MSN and Kit/Configuration The kits and configurations applicable to these MSNs are given at the end of this list: 0162 0172 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251 0254 0257 0260 0264 0267 0273 0278 0281 0283 0288 0291 0293 0297 0300 0309 0316 0318 0320 0326 0331 0333 0335 0338-0339 0342-0343 0345-0346 0349 0353 0355-0357 0359-0360 0362 0364 0367 0369 0372 0375 0379 0386 0394

NOTE : Config. 01 is applicable to aircraft that do not have Mod. No. 05891H5128 (SB A310-57-2020) embodied. JAV 0357 0481 KAC 0647 0649 0663 KYV 0172 MGL 0526 MPD 0451 0455 0642 MPJ 0410 MWA 0652 PIA 0585 0587 0590 0653 0656 0660 0676 0678 0682 0687 0689 0691 QAF 0473 QSC 0620 R1T 0591 RJA 0416 0445 0490 0491 0531 ROT 0636 0644 RZO 0571 0651 0661 S8G 0300 SBI 0427 0430 0453 0468 0475 0486 0487 0520 SGX 0519 0562 SUD 0437 TAP 0483 0494 0495 0541 0565 0573 THY 0386 0476 0478 0480 0496 0497 0502 TSC 0447 0472 0485 0545 0547 0588 0595 0597 0599 0600 0658 UAE 0592 0622 0646 0667 UZB 0574 0576 0706 WHT 0448

KIT No. QTY PER A/C CONFIGURATION 01 OPERATOR MSN

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# @ A310 SERVICE BULLETIN

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved The kits and configurations applicable to these MSNs are given at the end of this list: 0303 0313

NOTE : Config. 02 is applicable to aircraft that have both Mod. No.5891H5128 (SB A310-57-2020) and SB A310-00-2024 (Mod. No. 10685D20756) embodied.

The kits and configurations applicable to these MSNs are given at the end of this list: 0370 0389-0390 0397 0400

NOTE : Config. 03 is applicable to aircraft that have Mod. 05891H5128 (SB A310-57-2020) embodied and do not have SB A310-00-2024 (Mod. No. 10685D20756) embodied.

The kits and configurations applicable to these MSNs are given at the end of this list: 0378 0392 0399 0406-0407 0410 0413

NOTE : Config. 04 is applicable to aircraft that have Mod. No. 05980H5130 embodied and and do not have Mod. No. 05981H5131 embodied.

The kits and configurations applicable to these MSNs are given at the end of this list: 0416 0418 0421-0422 0425 0428-0429 0431 0434 0436-0437 0439 0441 0444-0449 0451-0453 0455-0458 0467 0472-0473 0475-0476 0478 0480-0485 0488-0492 0494-0503 0519-0520 0522-0524 0526-0527 0531 0534-0535 0537-0539 0541-0542 0544-0545 0547-0552 0562 0564-0565 0567-0568 0571 0573-0574 0576 0585-0595 0597-0600 0620 0622 0624 0634 0636 0638 0640 0642 0644 0646-0654 0656 0658 0660-0661 0663 0665 0667 0669 0671-0672 0674 0676 0678 0680 0682 0684 0686-0687 0689 0691 0693 0695 0697-0698 0700 0702 0704 0706 KIT No. QTY PER A/C CONFIGURATION 02

KIT No. QTY PER A/C CONFIGURATION 03

KIT No. QTY PER A/C CONFIGURATION 04

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# @ A310 SERVICE BULLETIN

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved NOTE : Config. 05 is applicable to A310-300 aircraft that have Mod. No. 05981H5131 embodied.

The kits and configurations applicable to these MSNs are given at the end of this list: 0419 0427 0430 0454 0468 0486-0487

NOTE : Config. 06 is applicable to A310-200 aircraft that have Mod. No. 05981H5131 embodied.

(3) Spares None B. CONCURRENT REQUIREMENTS None C. REASON (1) History During structural testing of the wing, fatigue cracks were found that started from the attachment holes around the refuelling aperture in the wing top skin between ribs 13 and 14. On A310-200 aircraft modification 05891H5128 (Service Bulletin A310-57-2020) introduces a redesigned refuelling cap which does not require this type of attachment. It has a larger diameter aperture which removes the existing holes from which cracks originate. On some A310-200 and on all A310-300 aircraft production modifications 05980H5130 and 05981H5131 introduced a similar design of refuelling cap as that introduced by modification 05891H5128. The effectivity of this Service Bulletin has been extended to include all A310 aircraft upto the extended service goal (ESG). An ESG study has shown that aircraft after modifications 05891H5128, 05980H5130 and 05981H5131 will now need detailed visual inspections in the area of the refuelling aperture in the wing top skin between ribs 13 and 14. KIT No. QTY PER A/C CONFIGURATION 05

KIT No. QTY PER A/C CONFIGURATION 06

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# @ A310 SERVICE BULLETIN

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (2) Objective/Action For A310-200 aircraft that are before modification 05891H5128 (Service Bulletin A310-57-2020), this Service Bulletin requires mandatory High Frequency Eddy Current (HFEC) inspections to be carried out in order to detect cracks in the attachment holes around the overwing refuelling aperture. For A310-200 aircraft after modification 05891H5128 (Service Bulletin A310-57-2020) and modification 05981H5131 and all A310-300 aircraft, a detailed visual inspection is required of the external top skin in the immediate area surrounding the refuelling aperture and also internally for cracks in the adjacent stringer 7 and stringer 8. For A310-200 aircraft that are before modification 05891H5128 (Service Bulletin A310-57-2020), if cracks are found during the HFEC inspection from the attachment holes which extend away from the direction of the aperture, the embodiment of the modification in its standard form will not be possible. Remedial action will then consist of either a variation of Mod 05891H5128 (Service Bulletin A310-57-2020), for short cracks, or a repair involving a reinforcing plate for longer cracks. On A310-200 aircraft after modification 05891H5128 (Service Bulletin A310-57-2020) and modification 05981H5131 and all A310-300 aircraft, if cracks are found during the detailed visual inspections they must be reported to AIRBUS. Further advice from AIRBUS will be required before the next flight. (3) Advantages Timely detection of cracks may reduce the necessity of carrying out non standard repairs. When Service Bulletin A310-57-2020 (Mod. No. 05891H5128) has been accomplished, HFEC inspections are replaced by DVI. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : (1) Config. 01 (a) Drain and vent the fuel tanks (b) Get access to the tank bays (LH and RH) between rib 13 and rib 14. (c) Remove shield and adapter ring

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# @ A310 SERVICE BULLETIN

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (d) Inspect bolt holes for cracks using a Rotating Probe HFEC technique. (e) Repair if necessary. (f) Install adapter ring and shield (g) Close up tanks (h) Refuel tanks (i) Carry out leak test. (j) Close up and complete the documentation. (2) Config. 02 thru Config. 06 (a) Drain and vent the fuel tanks (b) Get access to the tank bays (LH and RH) between rib 13 and rib 14. (c) Do a detailed visual inspection (DVI) of the LH and RH wing top skin between rib 13 and rib 14. (d) Do a DVI of the internal area for cracks on stringer 7 and stringer 8. (e) If necessary, report any cracks to AIRBUS and await further instructions. (f) Close up tanks (g) Refuel tanks (h) Carry out leak test. (i) Close up and complete the documentation. E. COMPLIANCE (1) Classification Mandatory (2) Accomplishment Timescale Accomplishment of this Service Bulletin is expected to be rendered mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). It is anticipated that the AD will confirm the thresholds and intervals given below but reference should be made to the AD for confirmation of the mandated accomplishment timescale. For Config. 01 Aircraft

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# @ A310 SERVICE BULLETIN

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved A Rotating Probe HFEC inspection is necessary within 380FC or 770FH whichever comes first from receipt of this Service Bulletin at Revision 04 and without exceeding already planned inspections according to SB A310-57-2006 at revision 3. Repeat HFEC inspections are necessary at every 2,300FC or 4,600FH whichever comes first. For Config. 02 Aircraft A detailed visual inspection (DVI) on the top skin and internally on the stringers is necessary within 30,900FC or 61,900FH whichever comes first from embodiment of SB A310-57-2020 (Mod. No. 05891H5128). For aircraft that have exceeded this threshold the inspection is necessary within 1500 FC or 18 months, whichever comes first from receipt of this Service Bulletin at Revision 04. Repeat DVIs are necessary at every 11,300FC or 22,600FH whichever comes first. For Config. 03 A DVI on the top skin and internally on the stringers is necessary within 30,900FC or 61,900FH whichever comes first from embodiment of Mod. No. 05891H5128 (SB A310-57-2020). For aircraft that have exceeded this threshold the inspection is necessary within 1500 FC or 18 months, whichever comes first from receipt of this Service Bulletin at Revision 04. Repeat DVIs are necessary at every 12,000FC or 24,000FH whichever comes first. For Config. 04 and Config. 05 Aircraft Short Range A DVI on the top skin and internally on the stringers is necessary within 25,900FC or 72,500FH whichever comes first from aircraft delivery. For aircraft that have exceeded this threshold the inspection is necessary within 1500 FC or 18 months, whichever comes first from receipt of this Service Bulletin at Revision 04. Repeat DVIs are necessary at every 12,000FC or 33,600FH whichever comes first. For Config. 04 and Config. 05 Aircraft Long Range

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# @ A310 SERVICE BULLETIN

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved A DVI on the top skin and internally on the stringers is necessary within 18,800FC or 94,200FH whichever comes first from aircraft delivery. For aircraft that have exceeded this threshold the inspection is necessary within 1500 FC or 18 months, whichever comes first from receipt of this Service Bulletin at Revision 04. Repeat DVIs are necessary at every 9,400FC or 47,200FH whichever comes first. For Config. 06 A DVI on the top skin and internally on the stringers is necessary within 30,900FC or 61,900FH, whichever occurs first from aircraft delivery. For aircraft that have exceeded this threshold the inspection is necessary within 1500FC or 18 months, whichever occurs first from receipt of this Service Bulletin at Revision 04. Repeat DVI are necessary at every 12,000FC or 24,000FH, whichever occurs first. F. APPROVAL Approved under EASA Design Organisation Approval No. EASA.21J.031 If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator's circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc, and general administration work are also not included. Config. 01 HFEC Inspection Get access 20.0 Inspection 10.0 Close up 22.0 TOTAL MANHOURS 52.0 ELAPSED TIME (HOURS) 26.0

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# @ A310 SERVICE BULLETIN

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Config. 02 thru Config. 06 Detailed Visual Inspection

H. WEIGHT AND BALANCE Not changed I. ELECTRICAL LOAD DATA Not changed J. REFERENCES

Service Bulletin (SB): A310-57-2020 Service Bulletin (SB): A310-00-2024 K. PUBLICATIONS AFFECTED None L. INTERCHANGEABILITY/MIXABILITY None Get access 10.0 Inspection 0.5 Close up 10.0 TOTAL MANHOURS 20.5 ELAPSED TIME (HOURS) 11.0

Aircraft Maintenance Manual (AMM) : 24-00-00 28-10-00 28-11-00 28-11-22 28-12-00 28-25-00 Non destructive Testing Manual (NTM) : 51-10-01, Part 6 51-60-00, Part 6 51-90-00, Part 9 Structural Repair Manual (SRM) : 51-40-21 51-40-44 51-49-00 51-76-10 51-76-20

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# @ A310 SERVICE BULLETIN

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 2. MATERIAL INFORMATION A. MATERIAL — PRICE AND AVAILABILITY None B. INDUSTRY SUPPORT INFORMATION AIRBUS will not provide industry support for accomplishment of this Service Bulletin. C. LIST OF COMPONENTS None D. LIST OF MATERIALS — OPERATOR SUPPLIED (1) Consumable Materials

(2) Components None E. PARTS TO BE RE—IDENTIFIED BY THE OPERATOR None F. TOOLING — PRICE AND AVAILABILITY None G. SPECIAL TOOLS None DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C INST DISP

Fuel Tank Sealant Polysulfide 09-001 As required Fuel Tank Sealant Polysulfide 09-002 As required Corrosion Inhibiting Fillet Consistency 09-016 As required

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# @ A310 SERVICE BULLETIN

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved

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# @ A310 SERVICE BULLETIN

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL WARNING : MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE IN POSITION BEFORE YOU START A TASK ON OR NEAR : - THE FLIGHT CONTROLS - THE FLIGHT CONTROL SURFACES - THE LANDING GEAR AND THE RELATED DOORS - COMPONENTS THAT MOVE MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS. WARNING : MAKE SURE THAT THE GROUND SAFETY LOCKS ARE CORRECTLY INSTALLED ON THE LANDING GEAR. THIS PREVENTS UNWANTED MOVEMENT OF THE LANDING GEAR. WARNING : OBEY THE SAFETY PROCEDURES WHEN YOU DO WORK IN A FUEL TANK. THIS WILL PREVENT INJURY OR DAMAGE. WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. (1) Preparation (a) Config. 01 thru Config. 06 1 Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00 Page block 301). 2 Put access platforms in position below the access panels 540HB and 640HB on the LH and RH wings. 3 Defuel and ventilate the inner fuel tanks (Refer to AMM 28-25-00 Page block 301 and AMM 28-10-00 Page block 301). 4 Open the access panels 540HB and 640HB (Refer to AMM 28-11-22 Page block 401). (2) Standard Practices (a) For fastener removal and installation refer to SRM 51-40-21. (b) For fastener hole and drill data refer to SRM 51-40-44. (c) For fastener torque tightening refer to SRM 51-49-00. (d) For the repair of sealing refer to SRM 51-76-10.

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# @ A310 SERVICE BULLETIN

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (e) For the repair of integral tank sealing refer to SRM 51-76-20. B. INSPECTION NOTE : The worksteps that follow are applicable to the LH and RH wings. (1) Config. 01 Refer to Figure 1 , Sheet 1 (a) Remove and retain the six bolts which attach the shield and remove the shield. (b) Remove and retain the remaining six bolts and the adapter ring. (c) Clean the bolt holes. (d) Do a Rotating Probe HFEC inspection of the twelve bolt holes for cracks. (Refer to NTM 51-10-01 Part 6.) (e) If cracks are found refer to the Para 3.C.(1) REPAIR for repair instructions. (f) If no cracks are found and Mod 05891H5128 (Service Bulletin A310-57-2020) is not to be embodied : 1 Clean all remaining traces of sealant from the aperture skin rebate and the inside face of the reinforcing plate. 2 Clean sealant from the mating faces of the shield and adapter ring. 3 Repair any damaged protective treatments. 4 Assemble the adapter ring into the skin rebate with Fuel Tank Sealant Polysulfide (Mat No. 09-001) . Fit the six attachment bolts using Fuel Tank Sealant Polysulfide (Mat No. 09-001) . 5 Fill the cavity between the adapter ring and the aperture with Fuel Tank Sealant Polysulfide (Mat No. 09-002) , using an extrusion gun and compact with a plastic spatula. 6 While the sealant is still soft, assemble the shield after applying Fuel Tank Sealant Polysulfide (Mat No. 09-001) to the mating face of the flange. Attach with the remaining six bolts using Fuel Tank Sealant Polysulfide (Mat No. 09-001) . 7 Fill the skin rebate around the edge of the adapter ring with Corrosion Inhibiting Fillet Consistency (Mat No. 09-016) . 8 Make certain that the work areas are clean and clear of tools and miscellaneous items of equipment.

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# @ A310 SERVICE BULLETIN

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved 9 Refit the filler cap. (g) Report the details of all cracks found during the inspections to AIRBUS SEE82 giving crack dimensions, direction and hole positions, using copies of Figure 1 as a reporting form. (2) Config. 02 thru Config. 03 Refer to Figure 3 , Sheet 1 (a) External DVI 1 Do a visual inspection of the area shown. Be most careful to look for cracks between fasteners. (b) Internal DVI 1 From inside the wing tank, use a good safe light source and do a visual inspection of the stringer 7 and stringer 8 for cracks in the area of the overwing refuel aperture. Be most careful to look for cracks between fasteners. (c) If cracks are found, refer to REPAIR, paragraph 3.C.(2). (3) Config. 04 Refer to Figure 4 , Sheet 1 (a) External DVI 1 Do a visual inspection of the area shown. Be most careful to look for cracks between fasteners. (b) Internal DVI 1 From inside the wing tank, use a good safe light source and do a visual inspection of the stringer 7 and stringer 8 for cracks in the area of the overwing refuel aperture. Be most careful to look for cracks between fasteners. (c) If cracks are found, refer to REPAIR, paragraph 3.C.(3). (4) Config. 05 thru Config. 06 Refer to Figure 5 , Sheet 1 (a) External DVI 1 Do a visual inspection of the area shown. Be most careful to look for cracks between fasteners. (b) Internal DVI 1 From inside the wing tank, use a good safe light source and do a visual inspection of the stringer 7 and stringer 8 for cracks in the area of the overwing refuel aperture. Be most careful to look for cracks between fasteners.

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# @ A310 SERVICE BULLETIN

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved (c) If cracks are found, refer to REPAIR, paragraph 3.C.(4). C. REPAIR (1) Config. 01 Refer to Figure 2 , Sheet 1 (a) If cracks are confined to the inside edge of the bolt holes, extending from the bolt holes towards the cap aperture, Service Bulletin A310-57-2020 (Mod. No. 05891H5128) must be accomplished as soon as possible, within a maximum period of 190FC/380FH whichever comes first. If Service Bulletin A310-57-2020 (Mod. No. 05891H5128) is not accomplished immediately, a further NDT check must be done before accomplishment. This will ensure that the crack has not subsequently initiated from the other side of the bolt holes extending away from the aperture. If this has occurred, refer to paragraph 3.C.(1)(b) that follows. (b) If a crack is detected in a bolt hole extending away from the direction of the aperture, it must be repaired before the next flight. If it is assessed to be 1mm (0.04in) or less in length into the material beyond the bolt hole it can be blended as follows : 1 Refer to Service Bulletin A310-57-2020 and embody Mod 05891H5128, up to and including reworking of the refuelling aperture and removal of the reinforcing plate. 2 Carry out initial blending and recheck for crack removal using an Eddy Current pencil probe (Refer to NTM 51-60-00 Part 6) or fluorescent dye penetrant (Refer to NTM 51-90-00 Part 9). Continue blending until the crack is completely removed or a maximum depth of 1.5mm (0.06in) is reached. 3 If the crack is completely removed, within the maximum depth limit of 1.5mm (0.06in), extend the blending by removing a further 0.5mm (0.02in) of material to the maximum depth of 'D.'. 4 Complete the blending by profiling into the aperture surface of adjacent blending as necessary. The blended surface is to be smooth and have a polished surface. 5 Complete the embodiment of Mod 05891H5128 (Service Bulletin A310-57-2020) and in addition fill in the blended area with Fuel Tank Sealant Polysulfide (Mat No. 09-002) before fitting the new adapter. 6 If the crack is not completely removed when the limit depth of 1.5mm (0.06in) is reached, refer to paragraph 3.C.(1)(c) that follows. (c) Further repair instructions will be required from AIRBUS SER if :

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# @ A310 SERVICE BULLETIN

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved — any crack extends more than 1mm (0.04 in.) into the material beyond the hole — any crack is found to be still detectable after initial blending to a maximum depth of 1.5mm (0.06 in.). Report details of cracking giving crack dimensions, direction and hole positions using copies of Figure 1 as a reporting form to AIRBUS. (2) Config. 02 thru Config. 03 Refer to Figure 3 , Sheet 1 (a) External Detailed Visual Inspection 1 If any cracks are found in the inspection area, report details of cracking to AIRBUS for a suitable repair. Give the crack dimensions, direction and hole positions. (b) Internal Detailed Visual Inspection 1 If the stringer 7 or stringer 8 is found to have cracks, report details of cracking to AIRBUS for a suitable repair. Give the crack dimensions, direction and hole positions. (3) Config. 04 Refer to Figure 4 , Sheet 1 (a) External Detailed Visual Inspection 1 If any cracks are found in the inspection area, report details of cracking to AIRBUS for a suitable repair. Give the crack dimensions, direction and hole positions. (b) Internal Detailed Visual Inspection 1 If the stringer 7 or stringer 8 is found to have cracks, report details of cracking to AIRBUS for a suitable repair. Give the crack dimensions, direction and hole positions. (4) Config. 05 thru Config. 06 Refer to Figure 5 , Sheet 1 (a) External Detailed Visual Inspection 1 If any cracks are found in the inspection area, report details of cracking to AIRBUS for a suitable repair. Give the crack dimensions, direction and hole positions. (b) Internal Detailed Visual Inspection 1 If the stringer 7 or stringer 8 is found to have cracks, report details of cracking to AIRBUS for a suitable repair. Give the crack dimensions, direction and hole positions.

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# @ A310 SERVICE BULLETIN

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved D. TEST None E. CLOSE UP (1) Config. 01 thru Config. 06 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Close the access panels 540HB and 640HB, AMM 28-11-22 Page block 401. (c) Remove the access platforms. (d) Remove all the warning notices that were positioned from the Accomplishment Instructions. (e) Refuel the fuel tanks (Refer to AMM 28-25-00 Page block 301). (f) Do a fuel leak test (Refer to AMM 28-11-00 Page block 501). (g) Put the aircraft back to normal operational conditions. F. DOCUMENTATION Write in the applicable aircraft records that you have done all the work given in the Service Bulletin.

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# @ A310 SERVICE BULLETIN

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Figure 1 Sheet 1 Config. 01:View of Top Skin Rib 13-14

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# @ A310 SERVICE BULLETIN

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved Figure 2 Sheet 1 Config. 01:View of Typical Crack Locations

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# @ A310 SERVICE BULLETIN

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 3 Sheet 1 (Goto A3 section) Config. 02 thru 03:Inspection Area

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# @ A310 SERVICE BULLETIN

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 4 Sheet 1 (Goto A3 section) Config. 04:Inspection Area

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# @ A310 SERVICE BULLETIN

DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 5 Sheet 1 (Goto A3 section) Config. 05 and 06:Inspection Area

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# @ A310 SERVICE BULLETIN REPORTING SHEET

7 DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : 1 of 1 Printed in FRANCE © AIRBUS, 2007 All rights reserved TITLE : WINGS - INSPECT AREA AROUND OVERWING REFUELLING APERTURE AT RIBS 13-14 MODIFICATION No. : None

Please complete the appropriate item (A or B): A - SB WILL BE embodie d............. YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiment :..........................

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........................................ B - SB HAS BEEN embodied on aircraft :.....................

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........................................ Operator comments :..............................

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....................................... From Airline :................................. Name/Title :.................................. Signature :.............. Date :............. If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to next normal revision or prior to SB embodiment, please indicate required service: Either: Modification Operational Impact (MOI), if available. . YES/NO Or : Intermediate revision.
................ YES/NO Important Information: This SB will only be incorporated in your maintenance and operational documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With the next feasible revision, this will result in - updating of maintenance documentation to show pre and post SB data. - updating of maintenance and operational documentation to show post SB data after embodiment. If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically include them in the manual revisions. Refer to SIL 00-037 for detailed information. Please return this completed sheet to: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn: SDC32 Technical Data and Documentation Services FAX: (+33) 5 61 93 28 06 e-mail: sb.reporting@airbus.com or via your Resident Customer Support Office. Alternatively, SB lists via letters or fax are also accepted.

# @ A310 SERVICE BULLETIN QUALITY PERCEPTION FORM

7 DATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006 REVISION No. : 04 — May 21/07 Page : 1 of 1 Printed in FRANCE © AIRBUS, 2007 All rights reserved Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data that you provide us will be used to analyse areas of difficulties and to take corrective action to further improve the quality of our Service Bulletins. We thank you for the time you have taken in completing this form. (Please rate on a scale of 1 to 4, with 4 being the highest score) - Quality rating of this SB 4 3 2 1 - Quality rating of the Accomplishment Instructions 4 3 2 1 - Quality rating of the Illustrations 4 3 2 1 - Is this SB easy to understand ? Y / N If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short description of the issue. Planning Material Instructions X Effectivity X Kit content X Preparation X Reason X List of Materials X Mod/Inspection X Manpower Operator Supplied X Test X References X Re-identification X Close-Up X Publication X Tooling X Illustrations Comments :

Operator : Date: Name/Title : Please return this form to : AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC Attn : SEM4 Service Bulletins Management FAX : (33) 5 61 93 42 51 Or via your Resident Customer Support Office.@ A310SERVICE BULLETINDATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006REVISION No. : 04 — May 21/07 Page : 21/22Printed in FRANCE © AIRBUS, 2007 All rights reservedFigure 3 Sheet 1Config. 02 thru 03:Inspection Area@ A310SERVICE BULLETINDATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006REVISION No. : 04 — May 21/07 Page : 23/24Printed in FRANCE © AIRBUS, 2007 All rights reservedFigure 4 Sheet 1Config. 04:Inspection Area@ A310SERVICE BULLETINDATE : Aug 13/86 SERVICE BULLETIN No. : A310—57—2006REVISION No. : 04 — May 21/07 Page : 25/26Printed in FRANCE © AIRBUS, 2007 All rights reservedFigure 5 Sheet 1Config. 05 and 06:Inspection Area